Rocket Exhaust Plume Phenomenology by F. Simmons

This booklet offers with the phenomenology of rocket exhaust plumes because the ambitions of space-based surveillance platforms. themes comprise the actual and chemical techniques in rocket engines and their exhaust plumes, specifically regard to move homes, fuel dynamics, and radiative mechanisms which are accountable for the iteration of emission in rocket exhaust plumes at infrared and different wavelengths. - information and knowledge showing during this ebook are for informational reasons simply. AIAA and the writer aren't answerable for any harm or harm caused by use or reliance, nor do AIAA and the writer warrant that use or reliance can be unfastened from privately owned rights.

4. J. S. AFRPL-TR-74-65 (1974). 1. *Sources of such data are discussed in Chapter 14. References 37 Fig. 19. Shock wave attached to vehicle. 1 Origin of Emission Rocket exhaust plume emission is generally thermal in character, arising from changes in the internal energy of the constituent molecules, the products of combustion. Those changes in the molecular energy levels are accompanied by the emission of radiation, provided certain quantum-mechanicalconditions are met. A hierarchy of the emissive processes is schematically illustrated in Fig.

Afterburning ceases about that time in the trajectory when vehicle velocity matches exhaust velocity. At this time, the exhaust gases are being deposited in the atmosphere with no relative velocity. Consequently, the apparent intensity of the missile is a minimum, being due mostly to that from the intrinsic core. (Actually, the cessation of afterburning is a more complex process, as discussed in Sec. ) As the missile continues to accelerate, the relative velocity increases as the plume as a whole moves into the undisturbed atmosphere.

5 Multiple Nozzle Effects The preceding discussions in this chapter were concerned with the characteristics of plumes from a single-nozzle rocket engine. However, the power plants of the lower stages usually consist of multiple engines or thrust chamber and nozzle assemblies. At very low altitudes, the plumes appear as separate streams without much interaction. However, as the missile rises, the plumes expand and interact to form a more complex flow-field. 13 shows two composite photographs of a model engine with two nozzles, fired in an altitude chamber.